EP2551592A3 - Microcircuit cooling for gas turbine engine combustor - Google Patents
Microcircuit cooling for gas turbine engine combustor Download PDFInfo
- Publication number
- EP2551592A3 EP2551592A3 EP12178487.0A EP12178487A EP2551592A3 EP 2551592 A3 EP2551592 A3 EP 2551592A3 EP 12178487 A EP12178487 A EP 12178487A EP 2551592 A3 EP2551592 A3 EP 2551592A3
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- turbine engine
- engine combustor
- microcircuit cooling
- microcircuit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001816 cooling Methods 0.000 title 1
- 239000003870 refractory metal Substances 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00018—Manufacturing combustion chamber liners or subparts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03042—Film cooled combustion chamber walls or domes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
Abstract
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/193,696 US9057523B2 (en) | 2011-07-29 | 2011-07-29 | Microcircuit cooling for gas turbine engine combustor |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2551592A2 EP2551592A2 (en) | 2013-01-30 |
EP2551592A3 true EP2551592A3 (en) | 2017-05-17 |
EP2551592B1 EP2551592B1 (en) | 2020-09-02 |
Family
ID=46639349
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12178487.0A Active EP2551592B1 (en) | 2011-07-29 | 2012-07-30 | Microcircuit cooling for gas turbine engine combustor |
Country Status (2)
Country | Link |
---|---|
US (2) | US9057523B2 (en) |
EP (1) | EP2551592B1 (en) |
Families Citing this family (60)
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JP5924618B2 (en) * | 2012-06-07 | 2016-05-25 | 川崎重工業株式会社 | Fuel injection device |
EP2956257B1 (en) * | 2013-02-12 | 2022-07-13 | Raytheon Technologies Corporation | Gas turbine engine component cooling passage and space eating core |
CA2904200A1 (en) * | 2013-03-05 | 2014-09-12 | Rolls-Royce Corporation | Dual-wall impingement, convection, effusion combustor tile |
EP2789915A1 (en) * | 2013-04-10 | 2014-10-15 | Alstom Technology Ltd | Method for operating a combustion chamber and combustion chamber |
EP3019704B1 (en) | 2013-07-12 | 2020-11-25 | United Technologies Corporation | Gas turbine engine component cooling with resupply of cooling passage |
WO2015023764A1 (en) * | 2013-08-16 | 2015-02-19 | United Technologies Corporation | Gas turbine engine combustor bulkhead assembly |
WO2015031816A1 (en) * | 2013-08-30 | 2015-03-05 | United Technologies Corporation | Gas turbine engine wall assembly with support shell contour regions |
WO2015030927A1 (en) | 2013-08-30 | 2015-03-05 | United Technologies Corporation | Contoured dilution passages for a gas turbine engine combustor |
WO2015050629A1 (en) * | 2013-10-04 | 2015-04-09 | United Technologies Corporation | Combustor panel with multiple attachments |
WO2015108584A2 (en) * | 2013-10-24 | 2015-07-23 | United Technologies Corporation | Passage geometry for gas turbine engine combustor |
EP3071884B1 (en) | 2013-11-18 | 2019-09-04 | United Technologies Corporation | Swept combustor liner panels for gas turbine engine combustor |
US10598379B2 (en) * | 2013-11-25 | 2020-03-24 | United Technologies Corporation | Film cooled multi-walled structure with one or more indentations |
EP3077641B1 (en) * | 2013-12-06 | 2020-02-12 | United Technologies Corporation | Cooling an igniter aperture body of a combustor wall |
US10378768B2 (en) | 2013-12-06 | 2019-08-13 | United Technologies Corporation | Combustor quench aperture cooling |
WO2015095759A1 (en) * | 2013-12-19 | 2015-06-25 | United Technologies Corporation | Thermal mechanical dimple array for a combustor wall assembly |
US10317079B2 (en) | 2013-12-20 | 2019-06-11 | United Technologies Corporation | Cooling an aperture body of a combustor wall |
EP3087266B1 (en) | 2013-12-23 | 2019-10-09 | United Technologies Corporation | Multi-streamed dilution hole configuration for a gas turbine engine and relating method of operation |
EP3090209B1 (en) * | 2014-01-03 | 2019-09-04 | United Technologies Corporation | A cooled grommet for a combustor wall assembly of a gas turbine |
WO2015117137A1 (en) * | 2014-02-03 | 2015-08-06 | United Technologies Corporation | Film cooling a combustor wall of a turbine engine |
US10112557B2 (en) * | 2014-04-03 | 2018-10-30 | United Technologies Corporation | Thermally compliant grommet assembly |
US9976743B2 (en) | 2014-07-03 | 2018-05-22 | United Technologies Corporation | Dilution hole assembly |
US9851105B2 (en) | 2014-07-03 | 2017-12-26 | United Technologies Corporation | Self-cooled orifice structure |
US10371381B2 (en) | 2014-07-22 | 2019-08-06 | United Technologies Corporation | Combustor wall for a gas turbine engine and method of acoustic dampening |
US9810148B2 (en) * | 2014-07-24 | 2017-11-07 | United Technologies Corporation | Self-cooled orifice structure |
EP2995863B1 (en) | 2014-09-09 | 2018-05-23 | United Technologies Corporation | Single-walled combustor for a gas turbine engine and method of manufacture |
US10731857B2 (en) | 2014-09-09 | 2020-08-04 | Raytheon Technologies Corporation | Film cooling circuit for a combustor liner |
EP3002518B1 (en) * | 2014-09-30 | 2019-01-30 | Ansaldo Energia Switzerland AG | Combustor front panel |
US10746403B2 (en) | 2014-12-12 | 2020-08-18 | Raytheon Technologies Corporation | Cooled wall assembly for a combustor and method of design |
US10132498B2 (en) * | 2015-01-20 | 2018-11-20 | United Technologies Corporation | Thermal barrier coating of a combustor dilution hole |
US9970299B2 (en) * | 2015-09-16 | 2018-05-15 | General Electric Company | Mixing chambers for turbine wheel space cooling |
US10099284B2 (en) | 2015-12-17 | 2018-10-16 | General Electric Company | Method and assembly for forming components having a catalyzed internal passage defined therein |
US9968991B2 (en) | 2015-12-17 | 2018-05-15 | General Electric Company | Method and assembly for forming components having internal passages using a lattice structure |
US10118217B2 (en) | 2015-12-17 | 2018-11-06 | General Electric Company | Method and assembly for forming components having internal passages using a jacketed core |
US9987677B2 (en) | 2015-12-17 | 2018-06-05 | General Electric Company | Method and assembly for forming components having internal passages using a jacketed core |
US10137499B2 (en) | 2015-12-17 | 2018-11-27 | General Electric Company | Method and assembly for forming components having an internal passage defined therein |
US10099276B2 (en) | 2015-12-17 | 2018-10-16 | General Electric Company | Method and assembly for forming components having an internal passage defined therein |
US10099283B2 (en) | 2015-12-17 | 2018-10-16 | General Electric Company | Method and assembly for forming components having an internal passage defined therein |
US10150158B2 (en) | 2015-12-17 | 2018-12-11 | General Electric Company | Method and assembly for forming components having internal passages using a jacketed core |
US10046389B2 (en) | 2015-12-17 | 2018-08-14 | General Electric Company | Method and assembly for forming components having internal passages using a jacketed core |
US9579714B1 (en) | 2015-12-17 | 2017-02-28 | General Electric Company | Method and assembly for forming components having internal passages using a lattice structure |
GB201603166D0 (en) * | 2016-02-24 | 2016-04-06 | Rolls Royce Plc | A combustion chamber |
US10286450B2 (en) | 2016-04-27 | 2019-05-14 | General Electric Company | Method and assembly for forming components using a jacketed core |
US10335853B2 (en) | 2016-04-27 | 2019-07-02 | General Electric Company | Method and assembly for forming components using a jacketed core |
US10358928B2 (en) | 2016-05-10 | 2019-07-23 | General Electric Company | Airfoil with cooling circuit |
US10704395B2 (en) | 2016-05-10 | 2020-07-07 | General Electric Company | Airfoil with cooling circuit |
US10415396B2 (en) | 2016-05-10 | 2019-09-17 | General Electric Company | Airfoil having cooling circuit |
US10731472B2 (en) | 2016-05-10 | 2020-08-04 | General Electric Company | Airfoil with cooling circuit |
US10544683B2 (en) | 2016-08-30 | 2020-01-28 | Rolls-Royce Corporation | Air-film cooled component for a gas turbine engine |
US10519780B2 (en) | 2016-09-13 | 2019-12-31 | Rolls-Royce Corporation | Dual-walled components for a gas turbine engine |
US10508811B2 (en) | 2016-10-03 | 2019-12-17 | United Technologies Corporation | Circumferential fuel shifting and biasing in an axial staged combustor for a gas turbine engine |
US10739003B2 (en) | 2016-10-03 | 2020-08-11 | United Technologies Corporation | Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine |
US10731855B2 (en) | 2017-08-23 | 2020-08-04 | Raytheon Technologies Corporation | Combustor panel cooling arrangements |
US20190186739A1 (en) * | 2017-12-19 | 2019-06-20 | United Technologies Corporation | Apparatus and method for mitigating particulate accumulation on a component of a gas turbine engine |
US11090771B2 (en) * | 2018-11-05 | 2021-08-17 | Rolls-Royce Corporation | Dual-walled components for a gas turbine engine |
US11015807B2 (en) | 2019-01-30 | 2021-05-25 | Pratt & Whitney Canada Corp. | Combustor heat shield cooling |
US10953461B2 (en) | 2019-03-21 | 2021-03-23 | Raytheon Technologies Corporation | Investment casting method including forming of investment casting core |
US11391461B2 (en) * | 2020-01-07 | 2022-07-19 | Raytheon Technologies Corporation | Combustor bulkhead with circular impingement hole pattern |
US11560843B2 (en) * | 2020-02-25 | 2023-01-24 | General Electric Company | Frame for a heat engine |
CN116658932A (en) | 2022-02-18 | 2023-08-29 | 通用电气公司 | Combustor liner with dilution openings having swirl vanes |
CN114719293B (en) * | 2022-03-24 | 2023-05-26 | 西北工业大学 | Annular cavity afterburner structure |
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EP0709550A1 (en) * | 1994-10-31 | 1996-05-01 | General Electric Company | Cooled shroud |
EP1235032A2 (en) * | 2001-02-26 | 2002-08-28 | United Technologies Corporation | Low emissions combustor for a gas turbine engine |
EP1377140A2 (en) * | 2002-06-19 | 2004-01-02 | United Technologies Corporation | Improved film cooling for microcircuits |
EP1375824A2 (en) * | 2002-06-19 | 2004-01-02 | United Technologies Corporation | Linked, non-plugging cooling microcircuits |
EP1505257A2 (en) * | 2003-08-08 | 2005-02-09 | United Technologies Corporation | Gas turbine blade circuit cooling |
EP1635119A2 (en) * | 2004-09-09 | 2006-03-15 | United Technologies Corporation | Cooled turbine engine components |
EP2549186A2 (en) * | 2011-07-21 | 2013-01-23 | United Technologies Corporation | Multi-stage amplification vortex mixture for gas turbine engine combustor |
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-
2012
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-
2015
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EP0709550A1 (en) * | 1994-10-31 | 1996-05-01 | General Electric Company | Cooled shroud |
EP1235032A2 (en) * | 2001-02-26 | 2002-08-28 | United Technologies Corporation | Low emissions combustor for a gas turbine engine |
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Also Published As
Publication number | Publication date |
---|---|
US10094563B2 (en) | 2018-10-09 |
EP2551592A2 (en) | 2013-01-30 |
US20150184857A1 (en) | 2015-07-02 |
US9057523B2 (en) | 2015-06-16 |
EP2551592B1 (en) | 2020-09-02 |
US20130025288A1 (en) | 2013-01-31 |
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